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Rolls-Royce Crécy
Sir Henry Tizard, Chairman of the Aeronautical Research Committee (ARC), was a proponent of a high-powered "sprint" engine for fighter aircraft and had foreseen the need for such a powerplant as early as 1935 with the threat of German air power looming. It has been suggested that Tizard influenced his personal friend Harry Ricardo to develop what eventually became known as the Rolls-Royce Crecy. The idea was officially discussed for the first time at an engine sub-committee meeting in December 1935.
"The Chairman remarked that if it was the desire of the Air Ministry to develop a type of sprint engine for home defence....there was the question as to how far fuel consumption could be disregarded. Mr Ricardo had raised this point in a recent conversation by enquiring whether a high fuel consumption might not be permissible under certain circumstances, for if so, an investigation of the possibilities of the two-stroke petrol engine appeared to be attractive."
Previous experience gained between 1927 and 1930 using two converted Rolls-Royce Kestrel engines through an Air Ministry contract had proven the worth of further research into a two-stroke sleeve-valved design. Both these engines had initially been converted to diesel sleeve-valved operation with a lower power output than the original design being noted along with increased mechanical failures, although one converted Kestrel was subsequently used successfully by Captain George Eyston in a land-speed record car named Speed of the Wind. The second engine was further converted to petrol injection which then gave a marked power increase over the standard Kestrel. The first complete V12 engine was built in 1941, designed by a team led by Harry Wood with Eddie Gass as the Chief Designer. Bore was 5.1 in (129.5 mm), stroke 6.5 in (165.1 mm), compression ratio 7:1 and weight 1,900 lb (862 kg). The firing angle was 30 degrees BTDC, and 15 lbf/sq.in (100 kPa) supercharger boost was typical. First run on 11 April 1941, in bench-testing it produced 1,400 horsepower (1,000 kW); however, there were problems with vibration and the cooling of the pistons and sleeves. The thrust produced by the exceptionally loud two-stroke exhaust was estimated as being equivalent to a 30% increase in power at the propeller on top of the rated output of the engine. The power of the engine was interesting in its own right, but the additional exhaust thrust at high- speed and altitude could have made it a useful stop gap between engines such as the Rolls-Royce Merlin and anticipated jet engines. Serial numbers were even, Rolls-Royce practice being to have even numbers for clockwise rotating engines when viewed from the front. The reciprocating sleeve valves were open-ended rather than sealing in a junk head – the open end uncovered the exhaust ports high in the cylinder wall at the bottom of the sleeves' stroke, leaving the ports cut into the sleeve to handle the incoming charge only. They had a stroke of 30% of the piston travel at 1.950 in (49.5 mm) and operated 15 degrees in advance of the crankshaft. The Crecy sleeve valves were of similar construction but differed in their operation compared to the rotary sleeve valve design that was pioneered by Roy Fedden, and used successfully for the first time in an aircraft engine, the Bristol Perseus, in 1932. Unlike most two-stroke engines, supercharging was used rather than crankcase compression to force the charge into the cylinder – this also allowed for a conventional oil lubrication system instead of the total-loss type found in many two-stroke engines. Stratified charge was used where the fuel was injected into a bulb-like extension of the combustion chamber where the twin spark plugs ignited the rich mixture. Operable air-fuel ratios of from 15 to 23:1 were available to govern the power produced between maximum and 60%. The rich mixture maintained near the spark plugs reduced detonation allowing higher compression ratios or supercharger boost. Supercharger throttling was used as well to achieve idling. The supercharger throttles were novel vortex types, varying the effective angle of attack of the impeller blades from 60 to 30 degrees. This reduced the power required to drive the supercharger when throttled, and hence fuel consumption at cruising power. Later testing involved the use of an exhaust turbine which was a half-scale version of that used in the Whittle W.1 turbojet, the first British jet engine to fly. Unlike a conventional turbocharger the turbine was coupled to the engine's accessory driveshaft and acted as a power recovery device. It was thought that using the turbine would lower fuel consumption allowing the engine to be used in larger transport aircraft. This was confirmed during testing however failures due to severe overheating and drive shaft fractures were experienced.
Test summary Crecy 2 11 April 1941 October 1942 – December 1942 February 1943 – July 1943 March 1944 – July 1944 August 1944 – November 1944 March 1945 – April 1945 (Total hours: 461)
November 1941 July 1942 – August 1942 September 1942 – October 1942 (Total hours: 293)
July 1943 – February 1944 May 1944 – September 1944 November 1944 – February 1945 June 1945 – August 1945 (Total hours: 481)
September 1943 – March 1944 April 1944 June 1944 – September 1944 October 1944 – December 1945 (Total hours: 336)
August 1944 – February 1945 March 1945 – June 1945 July 1945 – September 1945 (Total hours: 166)
January 1945 – October 1945
The progress of jet engine development overtook that of the Crecy and replaced the need for this engine. As a result work on the project ceased in December 1945 at which point only six complete examples had been built, however an additional eight V-twins were built during the project. Crecy s/n 10 achieved 1,798 horsepower (1,341 kW) on 21 December 1944 which after adjustment for the inclusion of an exhaust turbine would have equated to 2,500 horsepower (1,900 kW). Subsequent single-cylinder tests achieved the equivalent of 5,000 brake horsepower (3,700 kW) for the complete engine. By June 1945 a total of 1,060 hours had been run on the V12 engines with a further 8,600 hours of testing on the V-twins. The fate of the six Crecy engines remains unknown. If the Crecy had flown it would have done so using a Hawker Henley, L3385 which was delivered to Hucknall for conversion on 28 March 1943. This aircraft remained at Hucknall until 11 September 1945 when it was scrapped without ever having the engine fitted. Two years prior to the Hawker Henley's arrival (Summer 1941) a Supermarine Spitfire Mk II, P7674 had been delivered to Hucknall and was fitted with a Crecy mock-up to enable cowling drawings and system details to be designed. It had also been agreed that the first production Spitfire Mk III would be delivered to Hucknall in early 1942 minus its Merlin engine for fitment of an airworthy Crecy; this delivery did not occur however. A Royal Aircraft Establishment report (No. E.3932) of March 1942 estimated the performance of the Spitfire fitted with a Crecy engine and also compared this to a Griffon 61-powered variant of the type. The report stated that the Crecy's maximum power output would be too much for the Spitfire airframe but that a derated version would have considerable performance gains over the Griffon-powered fighter.
Crecy
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